Fırlatma araçları için titreşim izolasyon sistemi.

In the frame of this thesis, novel vibration isolation systems for spaces launch vehicles are designed and verified by vibration tests in laboratory environment. Payloads, satellites or spacecraft, are exposed high level of vibration loads during launch. These vibration loads are transmitted from launch vehicle to the payload and may have a detrimental effect on the payload. Vibration isolation systems can be used at the payload-launch vehicle interface in order to reduce vibration environment of a payload. In this thesis, Dnepr launch vehicle and Sentinel-2 satellite are chosen as a case study, and system-level technical requirements for vibration isolation system are determined. The vibration isolator properties, which are stiffness, loss factor and number of isolators, are derived to meet system-level technical requirements by performing random response and harmonic response analyses using mathematical model. Then, six different vibration isolator concept are achieved utilizing topology optimization, compliant mechanisms and similar systems. The detailed design of three different vibration isolator alternatives are performed to achieve required stiffness and loss factor values. Stiffness and loss factor of vibration isolators are obtained by finite element analyses. Finally, the designed vibration isolation systems are verified by finite element analyses and vibration tests in laboratory environment.M.S. - Master of Scienc